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s 4.5.2.2 Constraints HMM Assessment Study Report: CDF-20(A) February 2004 page 368 of 422 Figure 4-104 shows a pictorial representation of the balance between all the constraints mentioned and in particular the contradictory one of safety, ∆V consumption and time used for the rendezvous. Unfeasible Un-Safety Risky RvD ∆V Costly Ideal Risky Ideal Costly Ideal Unfeasible Desired Desired Unfeasible Figure 4-104: R & D constraints RvD time To be able to elaborate a rendezvous strategy for the HMM, the past experience was reviewed. In general, there are similarities and differences of the lunar rendezvous with Mars rendezvous: they have the same purpose and target and they have the same physics and principles. However, they take place in different planetary scenarios and they use different sensors and actuators. The main conclusion drawn here is that the lunar rendezvous experience is not directly applicable to our problem. In particular, there is a very long distance component in all maneuvers established that leads to a time lag between Ground Segment and Astronauts that need to be properly addressed and accounted for. 4.5.2.3 Assumptions and trade-offs The two mission arcs of ascent and rendezvous are “apparently” independent. However, for humans missions the ascent arc is much connected to the rendezvous one; In fact, the ascent and rendezvous arcs are in some strategies and trade-offs the “same” arc.
s HMM Assessment Study Report: CDF-20(A) February 2004 page 369 of 422 The first trade-off studied is the selection of roles and responsibilities between the ascent vehicle MAV and the orbiter. There are two main options: • MAV passive target, orbiter active chaser. This option leads to a slow RvD with a low MAV precision injection. It has a medium to low autonomy and the ascent crew has a strong dependency from orbiter crew • MAV active chaser, orbiter passive target: This option leads to a fast RvD. It requires a high MAV precision injection. It leads to a high degrees of autonomy. For safety reasons, the second option was selected. Hence, the MAV is the active chaser, and the orbiter is the passive target. However, both vehicles will remain three-axis stabilized during all maneuvres. The second trade-off is about the establishment of the rendezvous manoeuvring strategy. There are in essence three possible strategies: direct rendezvous, long rendezvous and short rendezvous. These are as shown in Figure 4-105. Direct Rv Long Rv Short Rv Rv Point Rv Point • 1 1 ascent ascent arc arc • 1 1 orbit orbit arc arc • 2 2 ascent ascent arcs arcs • 1 1 intermediate intermediate orbit orbit • 1 1 orbit orbit arc arc Figure 4-105: Rendezvous strategies Rv Point • 1 1 Lambert Lambert arc arc • N-times N-times times MCC MCC • 1 1 orbit orbit arc arc The Figure 4-106 and Figure 4-107 provide a list of the advantages and disadvantages of each of these strategies.
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s HMM Assessment Study Report: CDF-
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s STUDY TEAM HMM Assessment Study R
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s T A B L E O F C O N T E N T S HMM
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s L I S T O F F I G U R E S HMM Ass
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s L I S T O F T A B L E S HMM Asses
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s 1 INTRODUCTION 1.1 Background HMM
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s 2 GENERAL ARCHITECTURE 2.1 Study
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s 2.2.4.2 Accelerations HMM Assessm
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s 2.2.4.4 Temperature and relative
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s Figure 2-10: Trajectory Overview
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s 2.4.3.5 TEI and planetary protect
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s Mars Excursion Vehicle Transfer H
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s 2.7.5.1 Mission elements dry mass
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s 2.7.5.8 MEV release The MEV is re
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s Total mission time (days) 1200 10
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s stack 9 Propellant mass of the ne
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s The core supporting structure has
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s 2.7.7.1.3 Mars excursion module S
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s 2.7.7.1.4 Earth return capsule HM
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s Mission Phase Description Event s
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s Mission Phase Description Event s
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s 2.7.10 Mission performance Table
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s Days on Martian surface 450 400 3
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s Maximum manoeuvre duration 6 mont
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s % of loss from baseline 20 18 16
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s 2.7.15 Sensitivity analysis HMM A
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s 2.7.15.4 Influence of the mass of
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s Parameters used: • No Shuttle
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s 2.8.3.3 Launch 3- Front node Figu
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s 2.10.1.4 Communications HMM Asses
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s 2.10.2.2.2 LEO assembly HMM Asses
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s Basic RF link Four 70-m Ka-band s
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s 3 TRANSFER VEHICLE 3.1 Systems…
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s Operational Requirements It shall
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s Trans Mars Injection Module Mars
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s Figure 3-2: Parallel configuratio
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s Figure 3-6: Global dimensions com
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s Front Node 3.2.3.1.3 EVA systems
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s Trans Mars Injection (three stage
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s Figure 3-16: Recommendations for
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s Factors to be considered Impacts
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s Figure 3-24: Baseline design back
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s Figure 3-26: Baseline design priv
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s Module part 3............= 0 m 3
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s 3.3.2.1 Requirements and design d
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s 3.3.3.1 Requirements and design d
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s flux [W/m2] 250 200 150 100 50 0
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s Figure 3-38: Power required to ma
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s 3.3.4.3 Assumptions and trade-off
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s 3.3.4.3.3 Power conditioning and
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s 3.3.5 AOCS HMM Assessment Study R
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s Configuration Length (m) Total ma
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s 3.3.5.5 ACS for TMI 1 st HMM Asse
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s 3.3.6.2 Baseline design HMM Asses
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s 5 Reduce 2dB pointing precision t
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s 70-m antenna 70-m antenna 3.3.7.5
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s Angular separation SEM > 10º SEM
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s Figure 3-63: Communications MEV/M
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s Element 1: Transfer Habitation Mo
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s Radiation Shielding Shielding Req
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s The propulsion system and its cha
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s Item Nr. Mass [kg] Margin [%] Mas
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s 3.4.4 Mechanisms HMM Assessment S
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s 4 MARS EXCURSION VEHICLE 4.1 Syst
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s Figure 4-2: Option 2: Vertical co
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s 4.3 Surface habitation module Fig
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s Figure 4-11: Section through the
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s 4.3.1.5.3 Top level Figure 4-20:
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s Schedule in hours for the most ac
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s 4.3.3.6 Waste production HMM Asse
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s Figure 4-26: Total pressure vs. O
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s ECLS system mass: Figure 4-27: Ma
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s Figure 4-28: Mars albedo (L), ars
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s sun flux (W/m2) 450 400 350 300 2
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s Insulation structure (external) F
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s cryocooler heat lift [W] cryocool
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s • a duty cycle value (duration
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s Figure 4-48: MAV Power Inputs HMM
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s 4.3.5.4.2 Power storage HMM Asses
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s Figure 4-52: Regenerative Fuel Ce
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s Figure 4-54: Solar irradiance on
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s 450.00 400.00 350.00 300.00 250.0
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s 4.3.6.1 Budgets HMM Assessment St
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s 8 APPENDIX C - ACRONYMS AAA Avion
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s MLI Multi-Layer Insulation MMH Mo
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